Turbine and aircraft

Abstract

The present application relates to a kind of turbine and aircraft, wherein turbine includes turbine rotor and turbine stator, turbine rotor includes first rotor blade group, second rotor blade group and rotor base plate, first rotor blade group, second rotor blade group are each arranged on rotor base plate, annular cavity is formed between first rotor blade group, second rotor blade group and rotor base plate, turbine stator includes first stator and second stator, first stator and second stator each include stator blade group and stator base plate, stator blade group is arranged on stator base plate, and stator blade group is arranged in annular cavity, the area formed by first stator around its axis and the area formed by second stator around its axis are both sector area, first stator and second stator can be detachably docked and form complete circular area after docking, first rotor blade group, second rotor blade group and rotor base plate are integrally formed, and stator blade group and stator base plate are integrally formed.The utility model effectively improves turbine efficiency.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular to a turbine and an aircraft. Background Technology

[0002] The turbine is a crucial component of a gas turbine engine, converting the kinetic and internal energy of high-temperature combustion gases into shaft work for rotating machinery. Operating at high speeds under high temperature and pressure conditions, the turbine is the power source of the gas turbine engine, and its design directly impacts the overall performance of the engine.

[0003] Existing turbine structures decompose each stage of stator and rotor into independent components. After assembling them into turbine assemblies, due to structural limitations, there are unavoidable losses such as tip leakage and stationary rotor clearance, resulting in low turbine efficiency. Summary of the Invention

[0004] To address the aforementioned technical problems, this invention provides a turbine and an aircraft that can improve turbine efficiency.

[0005] On one hand, the present invention provides a turbine, including a turbine rotor and a turbine stator. The turbine rotor includes a first rotor blade group, a second rotor blade group, and a rotor base disk. The first rotor blade group and the second rotor blade group are both disposed on the rotor base disk, and an annular cavity is formed between the first rotor blade group, the second rotor blade group, and the rotor base disk. The turbine stator includes a first stator and a second stator, each of which includes a stator blade group and a stator base disk. The stator blade group is disposed on the stator base disk and within the annular cavity. The area formed by the first stator around its axis and the area formed by the second stator around its axis are both fan-shaped areas. The first stator and the second stator are detachably connected and form a complete circular area after connection. The first rotor blade group, the second rotor blade group, and the rotor base disk are integrally formed, and the stator blade group and the stator base disk are integrally formed.

[0006] In one embodiment of the present invention, the turbine rotor further includes a first moving blade crown and a second moving blade crown. Both the first rotor blade group and the second rotor blade group include moving blades. The moving blades of the first rotor blade group are disposed between the rotor base disk and the first moving blade crown, and the moving blades of the second rotor blade group are disposed between the rotor base disk and the second moving blade crown.

[0007] In one embodiment of the present invention, the moving blade includes a first moving blade portion and a second moving blade portion, the first moving blade portion and the second moving blade portion having an included angle and a smooth transition, the direction of the smooth transition between the first moving blade portion and the second moving blade portion protruding is a first direction, and the moving blades of the first rotor blade group and the second rotor blade group are arranged in the same direction on the rotor base disk; the stator blade group includes stator blades, the stator blades including a first stator blade portion and a second stator blade portion, the first stator blade portion and the second stator blade portion having an included angle and a smooth transition, the direction of the smooth transition between the first stator blade portion and the second stator blade portion protruding is a second direction; the first direction and the second direction are opposite, and the first direction and the second direction are not along the axial direction of the turbine rotor.

[0008] In one embodiment of the present invention, any one of the stator blades is a target stator blade, the moving blade adjacent to the target stator blade in the first rotor blade group is a first target moving blade, the moving blade adjacent to the target stator blade in the second rotor blade group is a second target moving blade, the first stator blade portion of the target stator blade is disposed toward the second moving blade portion of the first target moving blade, and the second stator blade portion of the target stator blade is disposed toward the first moving blade portion of the second target moving blade.

[0009] In one embodiment of the present invention, the number of moving blades in the first rotor blade group, the number of moving blades in the second rotor blade group, and the number of stator blades in the stator blade group are the same. The moving blades are arranged in a circular array around the axis of the rotor base disk on the rotor base disk, and the stator blades are arranged in a circular array around the axis of the stator base disk on the stator base disk.

[0010] In one embodiment of the present invention, a first flow channel is formed between two adjacent moving blades in the first rotor blade group, a second flow channel is formed between two adjacent stator blades in the stator blade group, and a third flow channel is formed between two adjacent moving blades in the second rotor blade group. The first flow channel, the second flow channel, and the third flow channel are sequentially connected to form a working fluid flow channel.

[0011] In one embodiment of the present invention, the turbine stator further includes a first grate and a second grate, both of which are disposed on the stator base plate and located on both sides of the stator blade assembly. The first grate is correspondingly disposed with the first moving blade crown and forms a first end-sealing mechanism with the first moving blade crown. The second grate is correspondingly disposed with the second moving blade crown and forms a second end-sealing mechanism with the second moving blade crown.

[0012] In one embodiment of the present invention, the first stator is provided with a first stator cross section, and the second stator is provided with a second stator cross section. The first stator cross section and the second stator cross section are detachably connected. The shapes of the first stator cross section and the second stator cross section are the same as the shapes of the stator blades. The first stator cross section and the second stator cross section are located at the middle position of two adjacent stator blades.

[0013] In one embodiment of the present invention, the first stator cross section and the second stator cross section form a mating surface group, and two sets of the mating surface group are provided, the cross-sectional shapes of the two sets of the mating surface group are centrally symmetrical about the axis of the turbine stator.

[0014] On the other hand, an aircraft is provided, including the aforementioned turbine, the aircraft including an engine, the engine including a turbine casing and a turbine main shaft, a turbine stator disposed on the turbine casing, and a turbine rotor disposed on the turbine main shaft.

[0015] The technical solution of the present invention has the following advantages compared with the prior art:

[0016] The turbine rotor of this application has its first rotor blade group, second rotor blade group, and rotor base disk integrally formed, thus eliminating the phase installation error caused by the axial connection of the first rotor blade group and the second rotor blade group in the prior art, and improving turbine efficiency. In addition, the stator blade group and stator base disk of the first stator and the second stator are integrally formed, and the first stator and the second stator can be detachably docked in the annular cavity, which also eliminates the axial clearance problem that exists when the rotor and stator are axially connected in the traditional turbine structure, and eliminates the phenomenon of airflow leakage through the axial clearance, thereby optimizing the working fluid flow channel and further improving turbine efficiency. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the turbine structure of the present invention;

[0019] Figure 2 This is an exploded structural diagram of the turbine of the present invention;

[0020] Figure 3 This is a partial perspective sectional view of the turbine of the present invention;

[0021] Figure 4 yes Figure 3A magnified view of a portion of point A in the middle;

[0022] Figure 5 This is a schematic diagram of a half-section of the turbine of the present invention;

[0023] Figure 6 yes Figure 5 A magnified view of a portion of point B in the middle;

[0024] Figure 7 This is a schematic diagram of the turbine rotor of the turbine of the present invention;

[0025] Figure 8 This is an exploded structural diagram of the turbine stator of the turbine of the present invention.

[0026] Explanation of reference numerals on the accompanying drawings:

[0027] 1. Turbine rotor; 2. Turbine stator; 3. First rotor blade assembly; 4. Second rotor blade assembly; 5. Rotor base disk; 6. Annular cavity; 7. First stator; 8. Second stator; 9. Stator blade assembly; 10. Stator base disk; 11. First moving blade crown; 12. Second moving blade crown; 13. Moving blade; 14. First moving blade section; 15. Second moving blade section; 16. Stator blade; 17. First stator blade section; 18. Second stator blade section; 19. First flow channel; 20. Second flow channel; 21. Third flow channel; 22. Working fluid flow channel; 23. First grate tooth; 24. Second grate tooth; 25. First end sealing mechanism; 26. Second end sealing mechanism; 27. First stator cross-section; 28. Second stator cross-section; 29. ​​Butt joint assembly.

[0028] Example 1

[0029] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of the embodiments of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this invention, and not all embodiments. Based on the embodiments of this invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this invention.

[0030] Reference Figures 1 to 8As shown, the turbine of the present invention includes a turbine rotor 1 and a turbine stator 2. The turbine rotor 1 includes a first rotor blade group 3, a second rotor blade group 4, and a rotor base disk 5. The first rotor blade group 3 and the second rotor blade group 4 are both disposed on the rotor base disk 5. An annular cavity 6 is formed between the first rotor blade group 3, the second rotor blade group 4, and the rotor base disk 5. The turbine stator 2 includes a first stator 7 and a second stator 8. The first stator 7 and the second stator 8 each include a stator blade group 9 and a stator base disk 10. The stator blade group 9 is disposed on the stator base disk 10 and is disposed within the annular cavity 6. The area formed by the first stator 7 around its axis and the area formed by the second stator 8 around its axis are both fan-shaped areas. The first stator 7 and the second stator 8 are detachably connected and form a complete circular area after connection. The first rotor blade group 3, the second rotor blade group 4, and the rotor base disk 5 are integrally formed, and the stator blade group 9 and the stator base disk 10 are integrally formed.

[0031] To improve turbine efficiency, this application proposes a novel turbine structure. The turbine of this application includes a turbine stator 2 and a turbine rotor 1, specifically, as follows: Figure 2 As shown, the turbine rotor 1 includes a first rotor blade group 3, a second rotor blade group 4, and a rotor base disk 5. Both the first rotor blade group 3 and the second rotor blade group 4 are composed of multiple moving blades 13, and are mounted on the rotor base disk 5. An annular cavity 6 is formed between the first rotor blade group 3, the second rotor blade group 4, and the rotor base disk 5. The annular cavity 6 is used to accommodate the stator blade group 9 on the turbine stator 2. The first rotor blade group 3, the second rotor blade group 4, and the rotor base disk 5 are integrally formed, such as by forging and casting followed by machining. Therefore, when the turbine rotor 1 is integrally formed, the phase between the first rotor blade group 3 and the second rotor blade group 4 is a preset fixed phase (the phase value can be set according to actual needs), eliminating the phase installation error caused by the axial connection of the first rotor blade group 3 and the second rotor blade group 4 in the prior art, and avoiding the phase matching problem between the first rotor blade group 3 and the second rotor blade group 4. Furthermore, the turbine stator 2 includes a first stator 7, a second stator 8, and a stator base disk 10, as shown in the figure. Figure 8As shown, both the first stator 7 and the second stator 8 include a stator blade assembly 9 and a stator base disk 10. The stator blade assembly 9 includes multiple stator blades 16. The stator blade assembly 9 is disposed on the stator base disk 10 and is integrally formed with the stator base disk 10. Since the first rotor blade assembly 3 and the second rotor blade assembly 4 on the turbine rotor 1 and the rotor base disk 5 are also integrally formed, in order to install the turbine stator 2 at a position that matches the turbine rotor 1, that is, the stator blade assembly 9 on the turbine stator 2 needs to be disposed in the annular cavity 6, the turbine stator 2 is divided into the first stator 7 and the second stator 8. The first stator 7 and the second stator 8 are detachably connected. Preferably, the first stator 7 and the second stator 8 are connected by tenon and mortise to achieve the alignment and installation of the turbine stator 2 and the turbine rotor 1. Furthermore, the area formed by the first stator 7 around its axis is a fan-shaped area, and the area formed by the second stator 8 around its axis is also a fan-shaped area. The first stator 7 and the second stator 8 are detachably connected, and after connection, they form a complete circular area. For example, the central angle of the fan-shaped area formed by the first stator 7 around its axis is 180°, and the central angle of the fan-shaped area formed by the second stator 8 around its axis is 180°, which adds up to 360°. This allows the stator blade groups 9 on the first stator 7 and the second stator 8 to be installed into the annular cavity 6. In addition, the turbine rotor 1 is not limited to having two rotor blade groups; it can also have three or more rotor blade groups. When the turbine rotor 1 has three rotor blade groups, there are two annular cavities 6 and two stator blade groups 9. One stator blade group is installed in one annular cavity, and the other stator blade group is installed in the other annular cavity; the case of multiple rotor blade groups follows the same principle. Since the first rotor blade group 3, the second rotor blade group 4, and the rotor base disk 5 of the turbine rotor 1 of this application are integrally formed, the phase installation error caused by the axial connection of the first rotor blade group 3 and the second rotor blade group 4 in the prior art is eliminated; and the stator blade group 9 of the first stator 7 and the stator base disk 10 of the second stator 8 are integrally formed, and the first stator 7 and the second stator 8 can be detachably connected in the annular cavity 6, thus eliminating the axial clearance problem that exists when the turbine rotor 1 and the turbine stator 2 are axially connected in the traditional turbine structure. Therefore, the phenomenon of airflow leakage through the axial clearance is eliminated, thereby optimizing the working fluid flow channel formed by the turbine rotor 1 and the turbine stator 2 and improving the turbine efficiency.

[0032] In this application, the first rotor blade group 3, the second rotor blade group 4, and the rotor base disk 5 of the turbine rotor 1 are integrally formed, thus eliminating the phase installation error caused by the axial connection of the first rotor blade group 3 and the second rotor blade group 4 in the prior art, and improving turbine efficiency. In addition, the stator blade group 9 of the first stator 7 and the stator base disk 10 of the second stator 8 are integrally formed, and the first stator 7 and the second stator 8 can be detachably connected in the annular cavity 6, which eliminates the axial clearance problem that exists when the turbine rotor 1 and the turbine stator 2 are axially connected in the traditional turbine structure, and eliminates the phenomenon of airflow leakage through the axial clearance, thereby optimizing the working fluid flow channel and further improving turbine efficiency.

[0033] In one embodiment, the turbine rotor 1 further includes a first moving blade crown 11 and a second moving blade crown 12. The first rotor blade group 3 and the second rotor blade group 4 both include moving blades 13. The moving blades of the first rotor blade group 3 are disposed between the rotor base disk 5 and the first moving blade crown 11, and the moving blades of the second rotor blade group 4 are disposed between the rotor base disk 5 and the second moving blade crown 12.

[0034] The turbine rotor 1 includes a first rotor blade group 3, a second rotor blade group 4, a rotor base disk 5, and moving blade crowns. The moving blade crowns include a first moving blade crown 11 and a second moving blade crown 12. The first moving blade crown 11 corresponds to the first rotor blade group 3, and the second moving blade crown 12 corresponds to the second rotor blade group 4. Figure 7 As shown, both the first rotor blade group 3 and the second rotor blade group 4 include moving blades 13. The moving blades of the first rotor blade group 3 are disposed between the rotor base disk 5 and the first moving blade crown 11, thereby forming a flow channel between the rotor base disk 5, the moving blades of the first rotor blade group 3, and the first moving blade crown 11. The moving blades of the second rotor blade group 4 are disposed between the rotor base disk 5 and the second moving blade crown 12, thereby forming a flow channel between the rotor base disk 5, the moving blades of the second rotor blade group 4, and the second moving blade crown 12, so that the high-temperature gas discharged from the combustion chamber can be converted into rotational kinetic energy after passing through the flow channel.

[0035] In one embodiment, the moving blade 13 includes a first moving blade portion 14 and a second moving blade portion 15, which are arranged at an angle and smoothly transition. The direction of the smooth transition between the first moving blade portion 14 and the second moving blade portion 15 is a first direction. The moving blades of the first rotor blade group 3 and the second rotor blade group 4 are arranged in the same direction on the rotor base disk 5. The stator blade group 9 includes a stator blade 16, which includes a first stator blade portion 17 and a second stator blade portion 18, which are arranged at an angle and smoothly transition. The direction of the smooth transition between the first stator blade portion 17 and the second stator blade portion 18 is a second direction. The first direction is opposite to the second direction, and the first direction and the second direction are not along the axial direction of the turbine rotor.

[0036] like Figure 4 As shown, the moving blade 13 includes a first moving blade portion 14 and a second moving blade portion 15, and there is an included angle between the first moving blade portion 14 and the second moving blade portion 15 to improve the efficiency of the high-temperature gas on the turbine blade, so that the high-temperature gas effectively drives the turbine rotor 1 to rotate; the included angle between the first moving blade portion 14 and the second moving blade portion 15 is smoothly transitioned, which conforms to aerodynamics, and the direction of the smooth transition between the first moving blade portion 14 and the second moving blade portion 15 is the first direction; in addition, the moving blades of the first rotor blade group 3 and the second rotor blade group 4 are arranged in the same direction on the rotor base disk 5, and the phase difference between the first rotor blade group 3 and the second rotor blade group 4 can be set according to actual needs to maximize the efficiency of the turbine. Figure 8 As shown, the stator blade assembly 9 includes stator blades 16, which have the same structure as the moving blades 13. The stator blade 16 includes a first stator blade portion 17 and a second stator blade portion 18, with an included angle between the first stator blade portion 17 and the second stator blade portion 18 to improve the efficiency of the high-temperature gas's action on the turbine blades, allowing the high-temperature gas to effectively drive the turbine rotor 1 to rotate. The included angle between the first stator blade portion 17 and the second stator blade portion 18 is smoothly transitioned, conforming to aerodynamics, and the direction of the smooth transition between the first stator blade portion 17 and the second stator blade portion 18 is a first direction bend. Furthermore, the first direction is opposite to the second direction, as shown... Figure 3 and Figure 4As shown, the direction of the smooth transition between the first moving blade portion 14 and the second moving blade portion 15 of the first rotor blade group 3 is the same as the direction of the smooth transition between the first moving blade portion 14 and the second moving blade portion 15 of the second rotor blade group 4, but opposite to the direction of the smooth transition between the first stator blade portion 17 and the second stator blade portion 18 of the stator blade group 9. This optimizes the working fluid flow channel 22, improves the efficiency of high-temperature gas driving blade rotation, and increases turbine efficiency. The first and second directions do not necessarily have to be arranged 180°, such as... Figure 4 The direction indicated by the hollow arrow in the dotted line is acceptable. The angle between the first and second directions, considering the vector direction, should be greater than 90° and not along the axis of the turbine rotor. The angle between the first and second directions, considering the vector direction, should facilitate the flow of air and facilitate the airflow to drive the turbine rotor to rotate.

[0037] In one embodiment, any one of the stator blades is a target stator blade, the moving blade adjacent to the target stator blade in the first rotor blade group 3 is a first target moving blade, the moving blade adjacent to the target stator blade in the second rotor blade group 4 is a second target moving blade, the first stator blade portion 17 of the target stator blade is disposed toward the second moving blade portion 15 of the first target moving blade, and the second stator blade portion 18 of the target stator blade is disposed toward the first moving blade portion 14 of the second target moving blade.

[0038] like Figure 4 As shown, a stator blade in any stator blade group 9 is selected as the target stator blade. The moving blade in the first rotor blade group 3 closest to the target stator blade is the first target moving blade, and the moving blade in the second rotor blade group 4 closest to the target stator blade is the second target moving blade. The target stator blade needs to coordinate with the first and second target moving blades according to a set direction to optimize the working fluid flow channel 22, improve the driving efficiency of the high-temperature gas flowing through the stator blade group 9 on the second target moving blade, and further improve the turbine efficiency. Specifically, as shown... Figure 4As shown, the orientation of the target stator blade and the first and second target moving blades is as follows: the first stator blade portion 17 of the target stator blade is positioned towards the second moving blade portion 15 of the first target moving blade, and the second stator blade portion 18 of the target stator blade is positioned towards the first moving blade portion 14 of the second target moving blade. Furthermore, the length of the first moving blade portion 14 is less than the length of the second moving blade portion 15, and the length of the first stator blade portion 17 is less than the length of the second stator blade portion 18. Therefore, when the high-temperature gas flows through the moving blade, it first contacts the shorter first moving blade portion 14, which guides the airflow at the inlet of the moving blade. Similarly, when the high-temperature gas flows through the stator blade 16, it first contacts the shorter first stator blade portion 17, which guides the airflow at the inlet of the stator blade 16. This allows for greater utilization of the kinetic energy of the high-temperature gas, thereby improving turbine efficiency.

[0039] In one embodiment, the number of moving blades in the first rotor blade group 3, the number of moving blades in the second rotor blade group 4, and the number of stator blades in the stator blade group 9 are the same. The moving blades 13 are arranged in a circular array around the axis of the rotor base disk 5 on the rotor base disk 5, and the stator blades 16 are arranged in a circular array around the axis of the stator base disk 10 on the stator base disk 10.

[0040] The number of moving blades in the first rotor blade group 3, the number of moving blades in the second rotor blade group 4, and the number of stator blades in the stator blade group 9 are the same, and as follows: Figure 7 and Figure 8 As shown, the moving blades 13 are arranged in a circular array around the axis of the rotor base disk 5, that is, the angle between any two adjacent moving blades about the axis of the rotor base disk 5 is the same; the stator blades 16 are arranged in a circular array around the axis of the stator base disk 10, that is, the angle between any two adjacent stator blades about the axis of the stator base disk 10 is the same; this ensures the uniformity of the working fluid flow channel 22 formed between the moving blades 13 and the stator blades, optimizes the working fluid flow channel 22, and effectively improves the efficiency of the turbine.

[0041] In one embodiment, a first flow channel 19 is formed between two adjacent moving blades in the first rotor blade group 3, a second flow channel 20 is formed between two adjacent stator blades in the stator blade group 9, and a third flow channel 21 is formed between two adjacent moving blades in the second rotor blade group 4. The first flow channel 19, the second flow channel 20 and the third flow channel 21 are sequentially connected to form a working fluid flow channel 22.

[0042] like Figure 4As shown, the turbine rotor 1 is provided with a first rotor blade group 3 and a second rotor blade group 4. A first flow channel 19 is formed between two adjacent moving blades on the first rotor blade group 3. The high-temperature and high-pressure gas flowing out of the combustion chamber first enters the first flow channel 19. The turbine stator 2 is provided with a stator blade group 9. A second flow channel 20 is formed between two adjacent stator blades on the stator blade group 9. The first flow channel 19 and the second flow channel 20 are connected. The high-temperature and high-pressure gas flowing out of the combustion chamber enters the first flow channel 19 and then enters the second flow channel 20. A third flow channel 21 is formed between two adjacent moving blades on the second rotor blade group 4. The third flow channel 21 is connected to the second flow channel 20. Therefore, the high-temperature and high-pressure gas flowing out of the combustion chamber passes through the first flow channel 19, the second flow channel 20 and the third flow channel 21 in sequence, and finally flows to the thrust nozzle to generate a reaction force to generate thrust. The first flow channel 19, the second flow channel 20, and the third flow channel 21 are sequentially connected to form the working fluid flow channel 22. The high-temperature and high-pressure gas flowing out of the combustion chamber drives the turbine rotor 1 to rotate after passing through the working fluid flow channel 22 and then enters the thrust nozzle. In addition, the surface of the rotor base 5 that forms the working fluid flow channel 22 is a smooth cylindrical surface to reduce the resistance to airflow.

[0043] In one embodiment, the turbine stator 2 further includes a first grate 23 and a second grate 24. The first grate 23 and the second grate 24 are both disposed on the stator base plate 10 and located on both sides of the stator blade assembly 9. The first grate 23 is radially opposite to the first moving blade crown 11 and the first grate 23 and the first moving blade crown 11 form a first end-sealing mechanism 25. The second grate 24 is radially opposite to the second moving blade crown 12 and the second grate 24 and the second moving blade crown 12 form a second end-sealing mechanism 26.

[0044] like Figure 5 and Figure 6As shown, the turbine stator 2 includes a stator base disk 10, a stator blade assembly 9, and grating teeth. The grating teeth include a first grating tooth 23 and a second grating tooth 24. The first grating tooth 23 and the second grating tooth 24 are both disposed on the stator base disk 10 and arranged circumferentially around the axis of the stator base disk 10. The first grating tooth 23 and the second grating tooth 24 are respectively located on both sides of the stator blade assembly 9. The first grate tooth 23 is radially opposite to the first moving blade crown 11, forming a first end-sealing mechanism 25; the second grate tooth 24 is radially opposite to the second moving blade crown 12, forming a second end-sealing mechanism 26. Therefore, the first end-sealing mechanism 25 and the second end-sealing mechanism 26 are arranged on both sides of the turbine stator 2, which can effectively reduce the leakage of gas inside the turbine. In addition, the structural installation method of the turbine rotor 1 and the turbine stator 2 also eliminates the axial clearance problem that exists when the turbine rotor 1 and the turbine stator 2 are axially connected in the traditional turbine structure, thus eliminating the phenomenon of airflow leakage through the axial clearance. Therefore, the existence of the end-sealing mechanism and the structural installation method of the turbine rotor 1 and the turbine stator 2 can effectively reduce the leakage of gas inside the turbine and effectively improve the turbine efficiency.

[0045] In one embodiment, the first stator 7 is provided with a first stator cross section 27, and the second stator 8 is provided with a second stator cross section 28. The first stator cross section 27 and the second stator cross section 28 are detachably connected. The shapes of the first stator cross section 27 and the second stator cross section 28 are the same as the shape of the stator blade 16. The first stator cross section 27 and the second stator cross section 28 are located at the middle position of two adjacent stator blades.

[0046] like Figure 8 As shown, the first stator 7 and the second stator 8 are detachably connected. Specifically, the first stator 7 has a first stator section 27, and the second stator 8 has a second stator section 28. The detachable connection between the first stator 7 and the second stator 8 is achieved through the detachable connection of the first stator section 27 and the second stator section 28, preferably using a tenon and mortise joint. To prevent the first stator section 27 and the second stator section 28 from damaging the structure of the complete stator blade 16, the shapes of the first stator section 27 and the second stator section 28 are the same as the shape of the stator blade 16. This way, the stator section does not pass through the stator blade 16, ensuring the integrity and strength of the stator blade 16. In addition, the first stator section 27 and the second stator section 28 are located in the middle position of two adjacent stator blades, which can improve the stability of the first stator section 27 and the second stator section 28, further improving the strength of the entire turbine stator 2.

[0047] In one embodiment, the first stator section 27 and the second stator section 28 form a mating surface group 29, and two sets of the mating surface group 29 are provided, with the cross-sectional shapes of the two sets of the mating surface group 29 being centrally symmetrical about the axis of the turbine stator 2.

[0048] like Figure 8 As shown, the turbine stator 2 includes a first stator 7 and a second stator 8. The first stator cross-section 27 on the first stator 7 and the second stator cross-section 28 on the second stator 8 form a stator cross-section group. Preferably, there are two groups of stator cross-sections on one turbine stator 2 to ensure that the first stator 7 and the second stator 8 can be detachably connected. Preferably, the cross-sectional shapes of the two groups of mating surfaces 29 are centrally symmetrical about the axis of the turbine stator 2. That is, the central angle of the fan-shaped area formed by the first stator 7 around its axis and the central angle of the fan-shaped area formed by the second stator 8 around its axis are both 180°, and the cross-sectional shapes of the two groups of mating surfaces 29 are centrally symmetrical about the axis of the turbine stator 2. This can effectively improve the strength and stability of the entire turbine stator 2.

[0049] Example 2

[0050] An aircraft is provided, including the aforementioned turbine. The aircraft includes an engine, which includes a turbine casing and a turbine main shaft. The turbine stator 2 is disposed on the turbine casing, and the turbine rotor 1 is disposed on the turbine main shaft.

[0051] The aircraft includes an engine, and a turbine is mounted on the engine and is a component of the engine. The engine includes a turbine casing and a turbine main shaft. The turbine includes a turbine rotor 1 and a turbine stator 2. The turbine rotor 1 is mounted on the turbine main shaft, and the turbine stator 2 is mounted on the turbine casing, thus achieving the alignment and installation of the turbine rotor 1 and the turbine stator 2. The turbine of this application includes a turbine rotor 1 and a turbine stator 2. The turbine rotor 1 includes a first rotor blade group 3, a second rotor blade group 4, and a rotor base disk 5. The first rotor blade group 3 and the second rotor blade group 4 are both disposed on the rotor base disk 5. An annular cavity 6 is formed between the first rotor blade group 3, the second rotor blade group 4, and the rotor base disk 5. The turbine stator 2 includes a first stator 7 and a second stator 8. The first stator 7 and the second stator 8 each include a stator blade group 9 and a stator base disk 10. The stator blade group 9 is disposed on the stator base disk 10 and is disposed within the annular cavity 6. The area formed by the first stator 7 around its axis and the area formed by the second stator 8 around its axis are both fan-shaped areas. The first stator 7 and the second stator 8 are detachably connected and form a complete circular area after connection. The first rotor blade group 3, the second rotor blade group 4, and the rotor base disk 5 are integrally formed, and the stator blade group 9 and the stator base disk 10 are integrally formed.

[0052] In this application, the first rotor blade group 3, the second rotor blade group 4, and the rotor base disk 5 of the turbine rotor 1 are integrally formed, thus eliminating the phase installation error caused by the axial connection of the first rotor blade group 3 and the second rotor blade group 4 in the prior art, and improving turbine efficiency. Furthermore, the stator blade group 9 of the first stator 7 and the stator base disk 10 of the second stator 8 are integrally formed, and the first stator 7 and the second stator 8 are detachably connected within the annular cavity 6, thereby eliminating the axial clearance problem that exists when the turbine rotor 1 and the turbine stator 2 are axially connected in the traditional turbine structure, eliminating the phenomenon of airflow leakage through the axial clearance, thus optimizing the working fluid flow channel 22, and further improving turbine efficiency. Moreover, the improvement in turbine efficiency can improve the flight power and performance of the entire aircraft.

[0053] Note that the above description is merely a preferred embodiment of the present invention and the technical principles employed. Those skilled in the art will understand that the present invention is not limited to the specific embodiments described herein, and various obvious changes, readjustments, and substitutions can be made without departing from the scope of protection of the present invention. Therefore, although the present invention has been described in detail through the above embodiments, the present invention is not limited to the above embodiments, and may include many other equivalent embodiments without departing from the concept of the present invention, the scope of which is determined by the scope of the appended claims.

Claims

1. A turbine, characterized in that: The system includes a turbine rotor (1) and a turbine stator (2). The turbine rotor (1) includes a first rotor blade group (3), a second rotor blade group (4), and a rotor base disk (5). The first rotor blade group (3) and the second rotor blade group (4) are both disposed on the rotor base disk (5). An annular cavity (6) is formed between the first rotor blade group (3), the second rotor blade group (4), and the rotor base disk (5). The turbine stator (2) includes a first stator (7) and a second stator (8). Both the first stator (7) and the second stator (8) include stator blade groups. (9) and stator base disk (10), the stator blade group (9) is disposed on the stator base disk (10), and the stator blade group (9) is disposed in the annular cavity (6). The area formed by the first stator (7) around its axis and the area formed by the second stator (8) around its axis are both fan-shaped areas. The first stator (7) and the second stator (8) are detachably connected and form a complete circular area after connection. The first rotor blade group (3), the second rotor blade group (4) and the rotor base disk (5) are integrally formed. The stator blade group (9) and The stator base disk (10) is integrally formed; the turbine rotor (1) further includes a first moving blade crown (11) and a second moving blade crown (12), the first rotor blade group (3) and the second rotor blade group (4) both include moving blades (13), the moving blades of the first rotor blade group (3) are disposed between the rotor base disk (5) and the first moving blade crown (11), and the moving blades of the second rotor blade group (4) are disposed between the rotor base disk (5) and the second moving blade crown (12); the turbine stator (2) further includes a first grating tooth (23). The first and second grating teeth (23) are both disposed on the stator base plate (10) and located on both sides of the stator blade group (9). The first grating tooth (23) is radially opposite to the first moving blade crown (11) and the first grating tooth (23) and the first moving blade crown (11) form a first end sealing mechanism (25). The second grating tooth (24) is radially opposite to the second moving blade crown (12) and the second grating tooth (24) and the second moving blade crown (12) form a second end sealing mechanism (26).

2. The turbine according to claim 1, characterized in that: The moving blade (13) includes a first moving blade portion (14) and a second moving blade portion (15). The first moving blade portion (14) and the second moving blade portion (15) are arranged at an angle and have a smooth transition. The direction of the smooth transition between the first moving blade portion (14) and the second moving blade portion (15) is a first direction. The moving blades of the first rotor blade group (3) and the second rotor blade group (4) are arranged in the same direction on the rotor base disk (5). The stator blade group (9) includes stator blades. The stator blades include a first stator blade portion (17) and a second stator blade portion (18). The first stator blade portion (17) and the second stator blade portion (18) are arranged at an angle and have a smooth transition. The direction of the smooth transition between the first stator blade portion (17) and the second stator blade portion (18) is a second direction. The first direction is opposite to the second direction, and the first direction and the second direction are not along the axis of the turbine rotor.

3. The turbine according to claim 2, characterized in that: Any of the stator blades is a target stator blade, the moving blade adjacent to the target stator blade in the first rotor blade group (3) is a first target moving blade, the moving blade adjacent to the target stator blade in the second rotor blade group (4) is a second target moving blade, the first stator blade portion (17) of the target stator blade is disposed toward the second moving blade portion (15) of the first target moving blade, and the second stator blade portion (18) of the target stator blade is disposed toward the first moving blade portion (14) of the second target moving blade.

4. The turbine according to claim 3, characterized in that: The number of moving blades in the first rotor blade group (3), the number of moving blades in the second rotor blade group (4), and the number of stator blades in the stator blade group (9) are the same. The moving blades (13) are arranged in a circular array around the axis of the rotor base disk (5) on the rotor base disk (5), and the stator blades are arranged in a circular array around the axis of the stator base disk (10) on the stator base disk (10).

5. The turbine according to claim 4, characterized in that: A first flow channel (19) is formed between two adjacent moving blades in the first rotor blade group (3), a second flow channel (20) is formed between two adjacent stator blades in the stator blade group (9), and a third flow channel (21) is formed between two adjacent moving blades in the second rotor blade group (4). The first flow channel (19), the second flow channel (20) and the third flow channel (21) are connected in sequence to form a working fluid flow channel (22).

6. The turbine according to claim 1, characterized in that: The first stator (7) is provided with a first stator cross section (27), and the second stator (8) is provided with a second stator cross section (28). The first stator cross section (27) and the second stator cross section (28) are detachably connected. The shape of the first stator cross section (27) and the second stator cross section (28) is the same as the shape of the stator blade. The first stator cross section (27) and the second stator cross section (28) are located in the middle position of two adjacent stator blades.

7. The turbine according to claim 6, characterized in that: The first stator section (27) and the second stator section (28) form a mating surface group (29). Two sets of the mating surface group (29) are provided, and the cross-sectional shapes of the two sets of the mating surface group (29) are centrally symmetrical about the axis of the turbine stator (2).

8. An aircraft, characterized in that: The aircraft includes a turbine as described in any one of claims 1 to 7, the aircraft includes an engine, the engine includes a turbine casing and a turbine main shaft, a turbine stator (2) is disposed on the turbine casing, and a turbine rotor (1) is disposed on the turbine main shaft.

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